Dual-redundancy all-electric brake control box with multiple actuators

Abstract

A dual-redundancy all-electric brake control box of multiple actuators comprises a printed board and a shell, the printed board is installed in the shell, and the dual-redundancy all-electric brake control box is characterized in that the printed board comprises a driving board, a control board, a power board and a connecting board, the driving board comprises a main driving board and a standby driving board, the control board comprises a main control board and a standby control board, and the power board is connected with the main control board. The main driving board is in communication connection with the main control board, the standby driving board is in communication connection with the standby control board, the control boards send control signals to the driving boards to control braking, the main control board and the standby control board are in communication connection with the flight control computer, and the main driving board and the standby driving board are electrically connected with the power board. The driving power source and the control power source are connected with the driving board and the control board through the connecting board and the power board, the main control board and the standby control board are in communication connection through a CAN protocol, when the main control board breaks down, the fault model is sent to a flight control computer, and the standby control board and the standby driving board are switched to control airplane wheels to brake.

Description

Technical Field

[0001] This invention relates to the field of aircraft braking system technology, and in particular to a dual-redundant all-electric brake control box with multiple actuators. Background Technology

[0002] All-electric braking represents the future of braking systems and is a crucial component of multi-electric aircraft. The dual-redundant all-electric brake control box, as an accessory to the brake control system, maximizes braking performance and shortens aircraft takeoff and landing distances. The anti-skid braking system plays a vital role in aircraft takeoff and landing, aiming to prevent tire blowouts during braking, reduce tire wear, and ensure safe takeoff and landing. Summary of the Invention

[0003] To address the problems mentioned in the background section, the present invention provides a dual-redundant all-electric brake control box with multiple actuators.

[0004] This invention discloses the following technical solution: a dual-redundant all-electric brake control box with multiple actuators, comprising a printed circuit board and a housing. The printed circuit board is installed inside the housing. The printed circuit board includes a drive board, a control board, a power board, and a connection board. The drive board includes a main drive board and a backup drive board. The control board includes a main control board and a backup control board. The main drive board is communicatively connected to the main control board, and the backup drive board is communicatively connected to the backup control board. The control board sends control signals to the drive board to control the braking. The main control board and the backup control board are communicatively connected to a flight control computer. The main drive board and the backup drive board are electrically connected to a power board. The drive power supply and the control power supply are connected to the drive board and the control board through the connection board and the power board. The main control board and the backup control board communicate using the CAN protocol.

[0005] Furthermore, the power board is also connected to the motor Hall sensor and force sensor for power supply. The motor is used to control the wheel brake. The drive board controls the motor to work and collects the signal from the motor Hall sensor. The control board collects the force sensor signal, wheel speed sensor signal, and main wheel grounding signal from the wheel brake device.

[0006] Furthermore, the housing includes a body and a cover plate, and the overlapping surfaces of the body and the cover plate are treated with conductive oxidation.

[0007] Furthermore, the control board and the flight control computer communicate using the RS422 protocol, and are connected via two RS422 buses that serve as backups for each other.

[0008] Furthermore, the driving power supply is 28V, and the control power supply is 28V.

[0009] Furthermore, the cover plate is mounted on the body by screws.

[0010] Beneficial effects: Compared with the prior art, the multi-actuator dual-redundant all-electric brake control box of the present invention independently controls the wheel brake by setting up two sets of control boards and drive boards. The main control board and the backup control board communicate using the CAN protocol. When the main control board fails, it sends the fault model to the flight control computer, switches the backup control board and backup drive board to control the wheel brake, and captures the phase information of the brake motor in real time through Hall sensor signals to realize the precise commutation action of the motor. Attached Figure Description

[0011] Figure 1 This is a block diagram showing the connection relationship of the control box in this invention; Figure 2 This is a block diagram illustrating the control principle of the control box of the present invention; Figure 3 This is a schematic diagram of the control box of the present invention; In the diagram: 1-body, 2-cover plate. Detailed Implementation

[0012] like Figures 1 to 3 As shown, a multi-actuator dual-redundant all-electric brake control box includes a printed circuit board (PCB) and a housing. The PCB is installed inside the housing. The PCB includes a drive board, a control board, a power board, and a connection board. The drive board includes a main drive board and a backup drive board, and the control board includes a main control board and a backup control board. The main drive board is communicatively connected to the main control board, and the backup drive board is communicatively connected to the backup control board. The control board sends control signals to the drive boards to control the brakes. The main control board and the backup control board are communicatively connected to a flight control computer, and the main drive board and the backup drive board are electrically connected to a power board. The drive power supply and the control power supply are connected to the drive board and the control board through the connection board and the power board, respectively. The drive power supply is 28V, and the control power supply is 28V. The main control board and the backup control board communicate using the CAN protocol. Both the main control board and the backup control board can independently control the braking devices of the left and right wheels. When the main control board malfunctions, it sends a fault signal to the flight control computer, and the flight control computer, upon receiving the fault signal, switches to the backup control board.

[0013] The power board is also connected to the motor Hall sensor and force sensor for power supply. The motor is used to control the wheel brakes. The drive board controls the motor to work and collects the signal from the motor Hall sensor. The control board collects the force sensor signal, wheel speed sensor signal, and main wheel grounding signal of the wheel brake device, and promptly obtains the wheel status feedback to the flight control computer. The braking strategy corresponding to the wheel status is adopted for braking. The control board and the flight control computer communicate using the RS422 protocol and are connected by two RS422 buses that are mutually redundant. Monitoring parameters, self-test data, and fault status can all be uploaded to the flight control computer.

[0014] The housing includes a body 1 and a cover plate 2. The overlapping surface of the body 1 and the cover plate 2 is treated with conductive oxidation to reduce the radiation interference of the all-electric brake control box to the outside. The cover plate 2 is installed on the body 1 with screws. The printed circuit board devices are spot-sealed and fixed with materials such as silicone rubber or epoxy to reduce vibration. Power devices or devices with high losses are installed close to the housing to effectively ensure heat dissipation. When installing the devices, thermal paste is evenly applied between the mounting surfaces of the devices and the housing to ensure good contact between the devices and the housing.

[0015] Working principle: The control box communicates with the flight control computer. The control box collects the wheel status and receives braking commands. The flight control computer calculates the braking amount and anti-skid amount based on the wheel status and sends the corresponding braking command to the control box. The brake control box controls the motor to work and brake. The all-electric brake control box communicates with the flight control computer, receives braking commands, and simultaneously collects wheel speed signals in real time. Based on the changes in the speed signals, it calculates the anti-skid amount during braking and anti-skid processes. It combines the braking amount corresponding to the braking command with the anti-skid amount and converts it into the desired braking force. The system outputs braking force through a pressure closed-loop dynamic adjustment based on the desired braking force and the feedback braking force.

[0016] The all-electric brake control box adopts a redundancy reconfiguration form: when the single actuator on the left fails, the symmetrical actuator on the right stops working, increases the output gain of other actuators, and ensures that the total braking capacity does not decrease. When both actuators on the left fail, the symmetrical actuator on the right stops working, and the normal actuator outputs braking force at the maximum non-locking output force, the specific value of which is based on the test results of the inertial table.

[0017] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A dual-redundant all-electric brake control box with multiple actuators, comprising a printed circuit board and a housing, wherein the printed circuit board is installed inside the housing, characterized in that: The printed circuit board includes a driver board, a control board, a power board, and a connection board. The driver board includes a main driver board and a backup driver board, and the control board includes a main control board and a backup control board. The main driver board is communicatively connected to the main control board, and the backup driver board is communicatively connected to the backup control board. The control board sends control signals to the driver board to control the braking. The main control board and the backup control board are communicatively connected to the flight control computer, and the main driver board and the backup driver board are electrically connected to the power board. The drive power supply and the control power supply are connected to the driver board and the control board through the connection board and the power board, respectively. The main control board and the backup control board communicate using the CAN protocol.

2. The dual-redundant all-electric brake control box with multiple actuators according to claim 1, characterized in that: The power board is also connected to the motor Hall sensor and force sensor for power supply. The motor is used to control the wheel brake. The drive board controls the motor to work and collects the signal from the motor Hall sensor. The control board collects the force sensor signal, wheel speed sensor signal, and main wheel grounding signal from the wheel brake device.

3. The dual-redundant all-electric brake control box with multiple actuators according to claim 1, characterized in that: The housing includes a body (1) and a cover plate (2), and the overlapping surfaces of the body (1) and the cover plate (2) are treated with conductive oxidation.

4. The dual-redundant all-electric brake control box with multiple actuators according to claim 1, characterized in that: The control board and flight control computer communicate using the RS422 protocol, and are connected via two RS422 buses that serve as backups for each other.

5. The dual-redundant all-electric brake control box with multiple actuators according to claim 1, characterized in that: The driving power supply is 28V, and the control power supply is 28V.

6. The dual-redundant all-electric brake control box with multiple actuators according to claim 3, characterized in that: The cover plate (2) is mounted on the body (1) by screws.

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